U.S. patent number 11,155,342 [Application Number 16/354,757] was granted by the patent office on 2021-10-26 for leading edge structure for a flow control system of an aircraft.
This patent grant is currently assigned to Airbus Operations GmbH. The grantee listed for this patent is Airbus Operations GmbH. Invention is credited to Alexander Buscher.
United States Patent |
11,155,342 |
Buscher |
October 26, 2021 |
Leading edge structure for a flow control system of an aircraft
Abstract
A leading edge structure (11) for a flow control system of an
aircraft (1) including a leading edge panel (13) surrounding
surrounds a plenum (17) which extends in a span direction (19),
wherein the leading edge panel (13) has a first side portion (21)
extending from a leading edge point (23) to a first attachment end
(25), wherein the leading edge panel (13) has a second side portion
(27) opposite the first side portion (21), extending from the
leading edge point (23) to a second attachment end (29), wherein
the leading edge panel (13) comprises an inner surface (33) facing
the plenum (17) and an outer surface (37) in contact with an
ambient flow (39), and wherein the leading edge panel (13)
comprises a plurality of micro pores (45) forming a fluid
connection between the plenum (17) and the ambient flow (39).
Inventors: |
Buscher; Alexander (Hamburg,
DE) |
Applicant: |
Name |
City |
State |
Country |
Type |
Airbus Operations GmbH |
Hamburg |
N/A |
DE |
|
|
Assignee: |
Airbus Operations GmbH
(Hamburg, DE)
|
Family
ID: |
65766879 |
Appl.
No.: |
16/354,757 |
Filed: |
March 15, 2019 |
Prior Publication Data
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Document
Identifier |
Publication Date |
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US 20190283866 A1 |
Sep 19, 2019 |
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Foreign Application Priority Data
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|
|
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Mar 15, 2018 [DE] |
|
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10 2018 106 064.5 |
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Current U.S.
Class: |
1/1 |
Current CPC
Class: |
B64C
3/28 (20130101); B64C 21/08 (20130101); B64C
5/02 (20130101); B64C 5/06 (20130101); B64C
21/04 (20130101); B64C 21/025 (20130101); B64C
21/06 (20130101); Y02T 50/10 (20130101); B64C
2230/22 (20130101); F15D 1/008 (20130101); B64C
2003/146 (20130101); B64C 2230/06 (20130101); B64C
2230/20 (20130101) |
Current International
Class: |
B64C
21/04 (20060101); B64C 5/06 (20060101); B64C
5/02 (20060101); B64C 21/02 (20060101); B64C
21/08 (20060101); B64C 21/06 (20060101); B64C
3/28 (20060101); F15D 1/00 (20060101); B64C
3/14 (20060101) |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
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2 208 669 |
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Jul 2010 |
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EP |
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2 886 453 |
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Jun 2015 |
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EP |
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Other References
European Search Report cited in EP 19162104.4 dated Jul. 15, 2019,
8 pages. cited by applicant .
German Search Report of DE 10 2018 106 064.5 dated Nov. 15, 2018, 9
pages. cited by applicant.
|
Primary Examiner: Green; Richard R.
Assistant Examiner: Gmoser; William L
Attorney, Agent or Firm: Nixon & Vanderhye P.C.
Claims
The invention claimed is:
1. A leading edge structure for a flow control system of an
aircraft comprising: a leading edge panel covering a plenum in a
curved manner, the plenum extending in a span direction of the
leading edge structure, wherein the leading edge panel has a first
side portion extending from a leading edge point to a first
attachment end, wherein the leading edge panel has a second side
portion, opposite the first side portion, extending from the
leading edge point to a second attachment end, wherein the leading
edge panel comprises an inner surface facing the plenum and an
outer surface in contact with an ambient flow, wherein the leading
edge panel comprises a plurality of micro pores forming a fluid
connection between the plenum and the ambient flow, wherein the
plenum is separated by a partition wall into a leading edge plenum
section aligned with the leading edge point, and a downstream
plenum section downstream from the leading edge plenum section,
wherein the leading edge plenum section is connected to a first air
inlet via a first duct, wherein the downstream plenum section is
connected to a second air inlet via a second duct, wherein the
first air inlet is separate from the second air inlet and the first
duct is separate from the second duct, and wherein the plenum is
configured to be at a pressure greater than a dynamic air pressure
of the ambient air flow over the outer surface.
2. The leading edge structure according to claim 1, wherein the
first air inlet and the first duct and/or the second air inlet and
second duct are configured to receive a mass flow of air to cause a
higher pressure in the leading edge plenum section as compared to
the downstream plenum section.
3. The leading edge structure according to claim 1, wherein the
first air inlet and/or the second air inlet is formed as a combined
air inlet/outlet device.
4. The leading edge structure according to claim 1, further
comprising a back wall connecting the first attachment end to the
second attachment end of the leading edge panel, thereby enclosing
the plenum on a side opposite the leading edge point.
5. The leading edge structure according to claim 1, wherein the
leading edge panel has a double-walled form including an inner wall
element having the inner surface and an outer wall element having
the outer surface.
6. The leading edge structure according to claim 5, wherein between
the inner and outer wall elements the leading edge panel comprises
a plurality of elongate stiffeners spaced apart from one another,
so that between each pair of adjacent stiffeners a hollow chamber
is formed between the inner and outer wall elements.
7. The leading edge structure according to claim 6, wherein the
outer wall element comprises the plurality of micro pores forming a
fluid connection between the hollow chambers and the ambient flow,
and wherein the inner wall element comprises openings forming a
fluid connection between the hollow chambers and the plenum.
8. A vertical tail plane for an aircraft comprising a vertical tail
plane box having a first lateral panel with a first attachment
portion and an opposite second lateral panel with a second
attachment portion, a leading edge structure according to claim 1,
wherein the first attachment end is attached to the first
attachment portion, and wherein the second attachment end is
attached to the second attachment portion, so that the first side
portion of the leading edge panel forms a continuous flow surface
with the first lateral panel of the vertical tail plane box, and
the second side portion of the leading edge panel forms a
continuous flow surface with the second lateral panel of the
vertical tail plane box.
9. The vertical tail plane according to claim 8, wherein the first
is arranged in the first lateral panel and the second air inlet is
arranged in the second lateral panel.
10. A leading edge structure for a lifting or air control structure
on an aircraft, the leading edge structure comprising: a leading
edge panel including a leading edge point region and first and
second side portions opposite to each other, and the first and
second side portions each extend in a chord-wise direction from the
leading edge point region, wherein the leading edge panel includes
an outer surface configured to be exposed to an ambient air flow
while the aircraft is in flight and an inner surface opposite to
the outer surface; a plenum within the leading edge panel and
facing the inner surface, wherein the plenum extends in a span-wise
direction through the leading edge structure; micro pores in the
leading edge panel and extending between the outer and inner
surfaces, wherein the micro pores form a fluid connection between
the plenum and the ambient flow; a partition wall separating a
leading edge plenum section of the plenum and a downstream plenum
section of the plenum, wherein the partition wall has a first edge
region and a second edge region, opposite to the first edge region,
wherein the first and second edge regions are attached to the inner
surface of the leading edge panel, and the partition wall is
impervious such that air in the leading edge plenum section does
not leak into downstream plenum section; a first air inlet
connected to the leading edge plenum via a first duct, and a second
air inlet connected to the downstream plenum via a second duct,
wherein the first air inlet is separate from the second air inlet
and the first duct is separate from the second duct; wherein the
leading edge plenum section is aligned with and adjacent the
leading edge point region and the downstream plenum section is
aligned with and adjacent at least one of the first and second side
portions, and wherein the plenum is configured to be at a pressure
greater than a dynamic air pressure of the ambient air flow over
the outer surface.
11. The leading edge structure of claim 10, wherein the lifting or
air control structure is a vertical tail plane.
12. The leading edge structure of claim 10, wherein the leading
edge plenum section is configured to be operated at a higher
internal air pressure than the downstream plenum section.
13. The leading edge structure of claim 10, further comprising: a
first ambient air inlet and a first duct extending between the
first ambient air inlet and the leading edge plenum section such
that ambient air entering the first ambient air inlet passes
through the first duct and pressurizes the leading edge plenum
section, and a second ambient air inlet and a second duct extending
between the second ambient air inlet and the downstream plenum
section such that ambient air entering the second ambient air inlet
passes through the second duct and pressurizes the downstream
plenum section to a pressure level lower than a pressure in the
leading edge plenum section.
14. A method of pressurizing a plenum in a leading edge structure
of a lifting or air control structure on an aircraft, wherein the
leading edge structure includes: a leading edge panel including a
leading edge point region and first and second side portions
opposite to each other, and the first and second side portions each
extend in a chord-wise direction from the leading edge point
region; wherein the leading edge panel includes an outer surface
configured to be exposed to an ambient air flow while the aircraft
is in flight and an inner surface opposite to the outer surface; a
plenum within the leading edge panel and facing the inner surface,
wherein the plenum extends in a span-wise direction through the
leading edge structure, micro pores in the leading edge panel and
extending between the outer and inner surfaces, wherein the micro
pores form a fluid connection between the plenum and the ambient
flow, and a partition wall separating a leading edge plenum section
of the plenum, and a downstream plenum section of the plenum,
wherein the partition wall has a first edge region and a second
edge region, opposite to the first edge region, wherein the first
and second edge regions are attached to inner surface of the
leading edge panel, and the partition wall is impervious such that
air in the leading edge plenum section does not leak into
downstream plenum section, wherein the leading edge plenum section
is aligned with and adjacent the leading edge point region and the
downstream plenum section is aligned with and adjacent at least one
of the first and second side portions, and the method comprises:
moving the leading edge structure through ambient air during fight
of the aircraft; pressurizing the leading edge plenum section to a
first pressure level which is greater than a dynamic air pressure
of the ambient air flowing over the outer surface at the leading
edge point region; and pressurizing the downstream plenum section
to a second pressure level which is greater than a dynamic pressure
of the ambient air flowing over the outer surface at the first
and/or second side portions, wherein the second pressure level is
less than the first pressure level.
15. The method of claim 14, further comprising: the pressurization
of the leading edge plenum section is performed by ducting ambient
air into a first ambient air inlet on the aircraft and into a first
duct extending between the first ambient air inlet and the leading
edge plenum section, and the pressurization of the downstream
plenum section is performed by ducting ambient air into a second
ambient air inlet on the aircraft and into a second duct extending
between the second ambient air inlet and the downstream plenum
section such that ambient air entering the second ambient air inlet
passes through the second duct and pressurizes the downstream
plenum section.
16. The leading edge structure of claim 1, wherein the leading edge
plenum section is sealed from the downstream plenum section such
that pressure in the leading edge plenum section does not affect
the pressure in the downstream plenum section.
17. The leading edge structure of claim 10, wherein the leading
edge plenum section is sealed from the downstream plenum section
such that pressure in the leading edge plenum section does not
affect the pressure in the downstream plenum section.
18. The method of claim 14, wherein the leading edge plenum section
is sealed from the downstream plenum section such that pressure in
the leading edge plenum section does not affect the pressure in the
downstream plenum section.
Description
RELATED APPLICATION
This application claims priority to German Patent Application DE 10
2018 106 064.5, filed Mar. 15, 2018, the entirety of which is
incorporated by reference.
FIELD OF INVENTION
The present invention relates to a leading edge structure for a
flow control system of an aircraft, in particular for a Hybrid
Laminar Flow Control system, where air is sucked in and blown out
of a porous surface of a flow body in order to extend the region of
laminar flow along the flow body. Further aspects of the present
invention relate to a vertical tail plane comprising such a leading
edge structure, and an aircraft comprising such a leading edge
structure or such a vertical tail plane. The leading edge structure
may be part of a horizontal tail plane or of a wing for an
aircraft.
BACKGROUND
The leading edge structure comprises a leading edge panel that
surrounds a plenum in a curved, e.g., arcuate, manner. The plenum
extends in a span direction through the leading edge structure.
When viewed in a cross section across the span direction, the
leading edge panel has a first side portion extending from a
leading edge point, i.e. from a fore tip of the leading edge
structure, to a first attachment end on a first side of the leading
edge structure. The leading edge point may extend as a line in a
span-wise direction along the leading edge panel. The first
attachment end being configured for attachment to a further
structure located downstream from the leading edge. Further, the
leading edge panel has a second side portion opposite the first
side portion. The second side portion extends from the leading edge
point to a second attachment end on a second side of the leading
edge structure opposite the first side. The second attachment end
being configured for attachment to a further structure downstream
from the leading edge.
The leading edge panel comprises an inner surface facing the plenum
and an outer surface in contact with an ambient flow. Further, the
leading edge panel comprises a plurality of micro pores, such as
perforations, forming a fluid connection between the plenum and the
ambient flow moving over an outer surface, e.g., skin, of the
leading edge panel. Air from the ambient flow can be sucked in
through the micro pores into the plenum. Pressurized air from the
plenum can be blown out through the micro pores into the ambient
flow.
Such leading edge structures are known in the art of hybrid laminar
flow control systems. For blowing out air from the plenum through
the micro pores into the ambient flow the pressure in the plenum
needs to be higher as the external pressure of the ambient flow
acting on the outer surface of the leading edge panel. As the
external pressure of the ambient flow has a maximum in the area of
the leading edge point where the incoming ambient flow impinges on
the outer surface of the leading edge panel in essentially
perpendicular manner, the required plenum pressure for blowing out
air is determined by the external pressure in the area of the
leading edge point.
SUMMARY OF INVENTION
An invention has been made and is disclosed here that provides an
efficient leading edge structure that is more precisely adapted to
the requirements. In the invention, the plenum is separated by a
partition wall into a leading edge plenum section in the area of
the leading edge point, and a downstream plenum section downstream
from the leading edge plenum section, i.e. further away from the
leading edge point. The invention takes advantage of a lower
pressure on the side portions of the leading edge structure which
are downstream in the ambient flow from the area of the leading
edge point. At these side portions the external pressure of the
ambient air is significantly lower than at the leading edge point.
Due to the reduced pressure at the side portions, the plenum
pressure needed to blow out air in these side portions is
significantly lower than the plenum pressure needed to blowout air
at the leading edge point.
In an embodiment of the invention, the partition wall may extend in
parallel to the span direction and is formed as a membrane e.g. of
fiber reinforced plastic. Both plenum sections may be sealed from
one another, so that the pressure in the leading edge plenum
section does not affect the pressure in the downstream plenum
section, e.g., in the side sections. In such a way, the plenum
pressure applied in the leading edge plenum section may be greater
than the plenum pressure in the downstream plenum section. This
allows the plenum pressure in the downstream plenum section(s) to
be adapted downstream along the first and second side portions of
the leading edge panel as required to overcome the external
pressure of the ambient flow. Specifically, in the downstream
plenum section a lower pressure can be applied as in the leading
edge plenum section, which in turn allows the downstream plenum
section and the associated inlet and duct parts to be designed with
minimum weight and space requirements and causes less aerodynamic
drag at the inlet.
The partition wall may be arranged at between 10% and 50% or
between 20% and 30% of the downstream length of the plenum,
measured from the leading edge point in the downstream
direction.
According to an embodiment, the leading edge plenum section is
connected to a first air inlet via a first duct for letting in air
from the ambient flow to the leading edge plenum section in order
to blow out air through the corresponding micro pores in connection
with the leading edge plenum section. The downstream plenum section
may be connected to a second air inlet via a second duct for
letting in air from the ambient flow to the downstream plenum
section in order to blow out air through the corresponding micro
pores in connection with the downstream plenum section. The first
air inlet may be separate from the second air inlet and the first
duct is separate from the second duct. In such a way, the first and
second air inlets and the first and second ducts can be formed
different from one another and can be adapted to the requirements
of the respective one of the leading edge plenum section and the
downstream plenum section.
In particular, the first air inlet and the first duct and/or the
second air inlet and second duct may be configured, e.g.,
positioned and dimensioned, for letting in such a mass flow rate
during flight of the associated aircraft that can cause a higher
pressure in the leading edge plenum section as in the downstream
plenum section, such as between 0% and 10% higher, between 1% and
7% higher, or between 2% and 5% higher. This means the air inlets
and ducts are adapted to the respective requirements in order to
increase efficiency of the leading edge structure.
The first air inlet and/or the second air inlet may be formed as a
combined, hybrid air inlet/outlet device configured for both
letting in air from the ambient flow and blowing out air into the
ambient flow. This can be done e.g. by the air inlet/outlet device
including a first flap that may open to the inside to form a
front-facing opening to let air in, and a second flap that may open
to the outside to form a rear-facing opening to let air out. First
and second flaps might be mounted to one another or share the same
parts. With such a combined air inlet/outlet device both inlet and
outlet function can be combined in one device so that no separate
air inlet and air outlet are necessary, thereby reducing
complexity, weight and space requirements of the leading edge
structure. Further, no sealing of a flap that is not in operation
has to be considered.
According to a further embodiment, the leading edge structure
further comprises a back wall connecting the first attachment end
to the second attachment end of the leading edge panel, thereby
enclosing the plenum, specifically the downstream plenum section,
on a side opposite the leading edge point. The back wall may be
parallel to the partition wall and is formed as a membrane e.g. of
fiber reinforced plastic.
According to an embodiment, the leading edge panel has a
double-walled form including an inner wall element having the inner
surface and, may be spaced apart from the inner wall element, an
outer wall element having the outer surface. Such a double-walled
form provides advantageous mechanical properties.
Between the inner and outer wall elements the leading edge panel
may comprise a plurality of elongate stiffeners connecting the
inner and outer wall elements and spaced apart from one another, so
that between each pair of adjacent stiffeners a hollow chamber is
formed between the inner and outer wall elements. The stiffeners
may be formed integrally with the inner wall element, extend in the
span direction, and have a solid and/or square-shaped or
trapezoid-shaped cross section. Further, the inner wall element may
be formed of a fiber reinforced plastic (FRP), the stiffeners are
formed as sandwich structures, and the outer wall element is formed
as a titanium or steel sheet. In such a way, a simple and reliable
double-walled structure is provided.
The outer wall element may comprise the plurality of micro pores
forming a fluid connection between the hollow chambers and the
ambient flow. In particular, the outer wall element comprises
multiple sections, wherein the porosity varies from one section to
another section in terms of pore diameter and/or pore pitch. The
inner wall element comprises openings forming a fluid connection
between the hollow chambers and the plenum, in particular between
the leading edge plenum section and the corresponding hollow
chambers, and between the downstream plenum section and the
corresponding hollow chambers. Each hollow chamber may comprise at
least one opening. The openings may be formed as throttle holes
having a predefined diameter adapted for a predefined mass flow
rate through the throttle holes in order to achieve a predefined
fluid pressure in the hollow chambers. Alternatively, the openings
might be formed as simple holes having such a diameter that
essentially the same pressure is present in the hollow chambers as
in the plenum.
The invention may be embodied in a vertical tail plane for an
aircraft. The vertical tail plane comprises a vertical tail plane
box and a leading edge structure according to any of the
embodiments described herein. The vertical tail plane box has a
first lateral panel with a first attachment portion and an opposite
second lateral panel with a second attachment portion. The first
attachment end of the leading edge structure is attached to the
first attachment portion and the second attachment end is attached
to the second attachment portion, so that the first side portion of
the leading edge panel forms a continuous flow surface with the
first lateral panel of the vertical tail plane box and the second
side portion of the leading edge panel forms a continuous flow
surface with the second lateral panel of the vertical tail plane
box. The features and advantageous described in connection with the
leading edge structure apply vis-a-vis to the vertical tail
plane.
According to an embodiment, the first air inlet and/or the second
air inlet is arranged in the first lateral panel and/or in the
second lateral panel and/or in another leading edge panel arranged
beside the leading edge structure in the span direction. The first
and second ducts may extend through the space between the vertical
tail plane box and other the leading edge panel. The first air
inlet and the second air inlet may be arranged on opposite sides of
the vertical tail plane.
An aircraft comprising a leading edge structure according to any of
the embodiments described herein, or comprising a vertical tail
plane according to any of the embodiment described herein. The
features and advantageous described in connection with the leading
edge structure apply vis-a-vis to the vertical tail plane.
SUMMARY OF DRAWINGS
An embodiment of the present invention is described hereinafter in
more detail by means of a drawing. The drawing shows in
FIG. 1 is a perspective view of an aircraft.
FIG. 2 is a side view of a vertical tail plane embodying the
invention, and
FIG. 3 is a cross sectional view across the span direction of a
leading edge structure embodying the invention.
DETAILED DESCRIPTION
FIG. 1 shows an aircraft 1 including a fuselage 3, wings 5, a
horizontal tail plane 7, and a vertical tail plane 9. The vertical
tail plane 9 is shown in more detail in FIG. 2. The vertical tail
plane 9 comprises a leading edge structure 11. The leading edge
structure 11 is shown in more detail in FIG. 3.
The leading edge structure 11 is configured for a hybrid laminar
flow control system and comprises a leading edge panel 13 and a
back wall 15. The leading edge panel 13 surrounds a plenum 17 in a
curved manner. The plenum 17 extends in a span direction 19 through
the leading edge structure 11. When viewed in a cross section
across the span direction 19, the leading edge panel 13 has a first
side portion 21 extending from a leading edge point 23 to a first
attachment end 25 on a first side of the leading edge structure 11.
Further, the leading edge panel 13 has a second side portion 27
opposite the first side portion 21, wherein the second side portion
27 extends from the leading edge point 23 to a second attachment
end 29 on a second side of the leading edge structure 11 opposite
the first side. The back wall 15 connects the first attachment end
25 to the second attachment end 29 of the leading edge panel 13,
thereby enclosing the plenum 17 on a side opposite the leading edge
point 23.
The leading edge panel 13 has a double-walled form including an
inner wall element 31 having an inner surface 33 facing the plenum
17, and an outer wall element 35 having an outer surface 37 in
contact with an ambient flow 39. Between the inner and outer wall
elements 31, 35 the leading edge panel 13 comprises a plurality of
elongate stiffeners 41 extending in the span direction 19 and
spaced apart from one another, so that between each pair of
adjacent stiffeners 41 a hollow chamber 43 is formed between the
inner and outer wall elements 31, 35. The stiffeners 41 are formed
integrally with the inner wall element 31 in a sandwich form and
have a solid, trapezoid-shaped cross section. The inner wall
element 31 is formed of a fiber reinforced plastic (FRP). The outer
wall element 35 is formed as a titanium sheet and comprises a
plurality of micro pores 45 forming a fluid connection between the
hollow chambers 43 and the ambient flow 39. The inner wall element
31 comprises openings 47 forming a fluid connection between the
hollow chambers 43 and the plenum 17.
As shown in FIG. 3, the plenum 17 is separated by a partition wall
49 into a leading edge plenum section 51 in the area of the leading
edge point 23, and a downstream plenum section 53 downstream from
the leading edge plenum section 51. The partition wall 49 extends
in parallel to the span direction 19 and is formed as a membrane of
fiber reinforced plastic. Both plenum sections 51, 53 are sealed
from one another, so that the pressure in the leading edge plenum
section 51 does not affect the pressure in the downstream plenum
section 53.
The leading edge plenum section 51 is connected to a first air
inlet 55 via a first duct 57 for letting in air from the ambient
flow 39 to the leading edge plenum section 51 in order to blow out
air through the corresponding micro pores 45 in connection with the
leading edge plenum section 51. Further, the downstream plenum
section 53 is connected to a second air inlet 59 via a second duct
61 for letting in air from the ambient flow 39 to the downstream
plenum section 53 in order to blow out air through the
corresponding micro pores 45 in connection with the downstream
plenum section 53. The first air inlet 55 is separate from the
second air inlet 59 and the first duct 57 is separate from the
second duct 61. The first air inlet 55 and the first duct 57 as
well as the second air inlet 59 and second duct 61 are configured
for letting in such a mass flow rate during flight of the aircraft
1 that causes a 3% higher pressure in the leading edge plenum
section 51 as in the downstream plenum section 53. The first air
inlet 55 and the second air inlet 59 are formed as combined air
inlet/outlet devices 63 configured for both letting in air from the
ambient flow 39 and blowing out air into the ambient flow 39.
As shown in FIGS. 2 and 3, the vertical tail plane 9 comprises a
vertical tail plane box 65 and the leading edge structure 11
mounted to the vertical tail plane box 65. The vertical tail plane
box 65 has a first lateral panel 67 with a first attachment portion
69 and an opposite second lateral panel 71 with a second attachment
portion 73. The first attachment end 25 of the leading edge
structure 11 is attached to the first attachment portion 69 and the
second attachment end 29 is attached to the second attachment
portion 73, so that the first side portion 21 of the leading edge
panel 13 forms a continuous flow surface with the first lateral
panel 67 of the vertical tail plane box 65 and the second side
portion 27 of the leading edge panel 13 forms a continuous flow
surface with the second lateral panel 71 of the vertical tail plane
box 65. The first air inlet 55 and the second air inlet 59 are
arranged on opposite sides in another leading edge panel 75 beside
the leading edge structure 11 with respect to the span direction
19. The first and second ducts 57, 61 extend through the space
between the vertical tail plane box 65 and the other leading edge
panel 75.
While at least one exemplary embodiment of the present invention(s)
is disclosed herein, it should be understood that modifications,
substitutions and alternatives may be apparent to one of ordinary
skill in the art and can be made without departing from the scope
of this disclosure. This disclosure is intended to cover any
adaptations or variations of the exemplary embodiment(s). In
addition, in this disclosure, the terms "comprise" or "comprising"
do not exclude other elements or steps, the terms "a" or "one" do
not exclude a plural number, and the term "or" means either or
both. Furthermore, characteristics or steps which have been
described may also be used in combination with other
characteristics or steps and in any order unless the disclosure or
context suggests otherwise. This disclosure hereby incorporates by
reference the complete disclosure of any patent or application from
which it claims benefit or priority.
* * * * *